Studies in Informatics and Control – ICI Bucharest
Kanthalakshmi SRINIVASAN1, Deepana GANDHI1, Manikandan VENUGOPAL2
1 Department of Instrumentation and Control Systems Engineering,
PSG College of Technology,
Coimbatore – 641004, India,
klakshmiramesh@yahoo.co.in, deepana.gandhi@gmail.com
2 Department of Electrical and Electronics Engineering,
Coimbatore Institute of Technology
Coimbatore – 641004, India,
manikantan-cit@gmail.com
Abstract: The orientation of a satellite in space described relative to some other object or system is known as the attitude of the satellite. The attitude may be changing with time. To be able to control the attitude of the satellite, it must be equipped with actuators that can produce the required torque. Control Moment Gyroscope is a space craft control actuator which acts as torque amplifier. It is suitable for three axis slew manoeuvring by providing the necessary torques via gimbaling a spinning flywheel. Control Moment Gyroscope is considered to be more efficient in terms of power consumption and slew rate. A major drawback encountered with the use of the Control Moment Gyroscope is the possibility of singularities for certain combinations of gimbal angles. The objective of this work is to detect these singularities so that robust steering laws can be developed.
Keywords: Control Moment Gyroscope, Gimbal angles, Singularities, Attitude Control, Steering laws.
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CITE THIS PAPER AS:
Kanthalakshmi SRINIVASAN, Deepana GANDHI, Manikandan VENUGOPAL, Spacecraft Attitude Control Using Control Moment Gyro Reconfiguration, Studies in Informatics and Control, ISSN 1220-1766, vol. 23 (3), pp. 285-296, 2014. https://doi.org/10.24846/v23i3y201407